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CN102213425B - Combustor liners for turbine engines - Google Patents

Combustor liners for turbine engines Download PDF

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Publication number
CN102213425B
CN102213425B CN201110087119.3A CN201110087119A CN102213425B CN 102213425 B CN102213425 B CN 102213425B CN 201110087119 A CN201110087119 A CN 201110087119A CN 102213425 B CN102213425 B CN 102213425B
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CN
China
Prior art keywords
liner
trailing
air deflector
sloped portion
cylindrical
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Fee Related
Application number
CN201110087119.3A
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Chinese (zh)
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CN102213425A (en
Inventor
R·J·奇尔拉
D·T·莱蒙
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General Electric Company PLC
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General Electric Co
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Filing date
Publication date
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Publication of CN102213425A publication Critical patent/CN102213425A/en
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Publication of CN102213425B publication Critical patent/CN102213425B/en
Expired - Fee Related legal-status Critical Current
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002—Wall structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/78—Other construction of jet pipes
    • F02K1/82—Jet pipe walls, e.g. liners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
    • F02K9/32—Constructional parts; Details not otherwise provided for
    • F02K9/34—Casings; Combustion chambers; Liners thereof
    • F02K9/346—Liners, e.g. inhibitors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03043—Convection cooled combustion chamber walls with means for guiding the cooling air flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03045—Convection cooled combustion chamber walls provided with turbolators or means for creating turbulences to increase cooling

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
  • Spray-Type Burners (AREA)

Abstract

The invention relates to a combustor liner for a turbine engine, particularly to a combustor liner for a turbine engine combustor, including a single-walled generally cylindrical liner 20 that extends from a head end to an aft end, a venturi 26 that is formed on the combustor liner at a location between the head and aft ends. The venturi is formed by a first inclined portion 73 of the single-walled liner that reduces in diameter while progressing in the aft direction and a second inclined portion 75 of the single-walled liner that increases in diameter while progressing in the aft direction. An aft end of the first inclined portion is joined to a head end of the second inclined portion.

Description

Combustion liner for turbogenerator
Technical field
The present invention relates to the combustion liner for turbogenerator.
Background technology
The turbogenerator that generates (for example, generating) industry for power generally include by a plurality of burners around compressor section.These burners become concentric ring around the disposed outside of compressor.Compressed air from compressor section is fed in burner, this its, mixes mutually with fuel.Then fuel-air mixture burns in burner, and in the turbine of the burning gases of heat introducing engine, in order to the motive power that makes turbine operation to be provided.
Typical turbogenerator burner can comprise combustion liner, the combustion zone that this bush ring burns therein around fuel-air mixture.The burner of some types is included in the Venturi tube (venturi) in combustion liner, and this Venturi tube is that the reduced diameter portion of combustion liner inside is divided substantially.
The reduced diameter portion of the formation Venturi tube of combustion liner divides common needs special cooling to prevent that the material that forms Venturi tube from being damaged by hot combustion gas.This realizes by double-walled structure is set conventionally, and in double-walled structure, the annular space that cooling-air is flowed through between the inner and outer wall of Venturi tube section is with cooling this venturi area under control section.Regrettably, this complex structure, and may be very difficult and expensive for manufacture.In addition, the complexity of double-walled Venturi tube section causes air leakage conventionally, and this can reduce the overall efficiency of turbine, also can cause producing undesirable combustion by-products.
Summary of the invention
On the one hand, the present invention is embodied in a kind of combustion liner for turbogenerator burner, and wherein, combustion liner is formed by the substantial cylindrical lining that extends to the single wall formula of tail end from head end.Combustion liner comprises the Venturi tube between head end and tail end that is formed on bush inside.Venturi tube is formed by the first sloping portion of single wall formula lining and the second sloping portion of single wall formula lining, wherein, the first sloping portion diameter when caudad direction (aft direction) is above extended reduces, and the second sloping portion diameter when caudad side extends upward increases.The tail end of the first sloping portion is attached on the head end of the second sloping portion.
On the other hand, the present invention is embodied in a kind of combustion liner for turbogenerator burner, and wherein, combustion liner is formed by the single wall formula lining that extends to tail end from head end.In single wall formula lining, between head end and tail end, form reduced diameter portion and divide, this reduced diameter portion is divided in the inside of lining formation Venturi tube.Air deflector (deflector) is arranged on the outside of single wall formula lining to have annular space between the inside of air deflector and the outside of lining.Air deflector flows through the outside along lining part air stream from tail end head-end deflects into insert diameter and reduces outside partly.
Accompanying drawing explanation
Fig. 1 is the sectional view that comprises the representative burner of combustion liner, and this combustion liner has double-walled Venturi tube;
Fig. 2 is the burner sectional view that comprises single wall formula combustion liner, and this single wall formula combustion liner has Venturi tube;
Fig. 3 is the sectional view of a part of an embodiment of single wall formula combustion liner, and this single wall formula combustion liner comprises air deflector;
Fig. 4 is the sectional view of a part of another embodiment of single wall formula combustion liner, and this single wall formula combustion liner comprises air deflector;
Fig. 5 is the sectional view of a part of another embodiment of single wall formula combustion liner, and this single wall formula combustion liner comprises air deflector;
Fig. 6 is the sectional view of a part of another embodiment of single wall formula combustion liner, and this single wall formula combustion liner comprises air deflector; And
Fig. 7 is the sectional view of a part for single wall formula combustion liner, and this single wall formula combustion liner comprises Venturi tube.
Parts List
Transition member 10
Compressor section 12
Combustion liner 20
Outer wall 21,22
Reduced diameter portion divides 22
Airport 23
Inwall 24
The annular space 25 of Venturi tube
Venturi tube section 26
Tail end 27
Flow sleeve 30
Burner housing 40
Main fuel spray nozzle 50
Auxiliary fuel nozzle 60
Deflector 70
Annular space 72 in deflector
Dilution holes 74
Flow spoiler ring 76
Combustion zone 95
The specific embodiment
Fig. 1 shows the sectional view for the representative burner of turbogenerator.Burner is positioned to the compressor section 12 of contiguous turbogenerator.Burner comprises transition member 10, and this transition member is led to the turbine of engine.Combustion liner 20 is connected in transition member 10.The combustion zone 95 that combustion liner 20 burns therein around fuel-air mixture.
At the head end of burner, a plurality of main fuel spray nozzles 50 are located with circular pattern around the periphery of burner.Burner also can comprise the pilot jet 60 that is positioned at burner central authorities.Fuel is delivered to the inside of combustion liner 20 by nozzle 50,60.
Flow sleeve 30 is around the location, outside of combustion liner 20.Burner housing 40 is around the outside of flow sleeve 30.Between the outside of combustion liner 20 and the inside of flow sleeve 30, form annular space.As shown by the arrows in Figure 1, from the compressed air of the compressor section 12 of turbogenerator, flow into and pass through this annular space.
Compressed air enters the tail end of the annular space between combustion liner 20 and flow sleeve 30, and then to the head end of burner, advances.When compressed air arrives head end, it turns to 180 ° and then enter the inside of combustion liner 20.Then compressed air mix mutually with the fuel of carrying by fuel nozzle 50,60, and fuel-air mixture burns in combustion zone 95.
As shown in Figure 1, Venturi tube 26 is positioned at the inside of combustion liner 20.Venturi tube 26 is by comprising inwall 24 and becoming the double-walled structure of angie type outer wall 21,22 to be formed.Thereby airport 23 is formed on into and in angie type outer wall 21/22, allows to flow through the air stream via hole 23 of the annular space between combustion liner 20 and flow sleeve 30 and enter in the one-tenth angie type outer wall 21/22 and the space between inwall 24 that is formed on Venturi tube 26.
The double-walled structure of Venturi tube is designed to help cooling Venturi tube 26, thereby prevents that Venturi tube is overheated and be damaged.As shown by the arrows in Figure 1, the air that flows through into the hole 23 in angie type outer wall 21/22 flows along the annular space between the inner and outer wall of Venturi tube, and the fuel-air mixture that finally burns in the tail end 27 of Venturi tube inwall 24 is discharged and is added in combustion liner 20 inside of this air.As a result, the final inside that allows air to enter combustion liner 20, the hole in the one-tenth angie type outer wall 21/22 of Venturi tube 23.
As mentioned above, for Venturi tube arranges comparatively costliness of this double-walled structure.Double-walled structure is difficult to manufacture, and owing to being used for forming a plurality of angles and the parts of this double-walled Venturi tube, therefore can there is leakage and the damage of each part.
Fig. 2 shows for comprising a kind of alternative construction of the combustion liner of Venturi tube.In this structure, comprise that the whole combustion liner of Venturi tube is formed by single wall-like structure, this list wall-like structure extends to tail end from the head end of burner.As shown in Figure 2, combustion liner 20 still by 30 of flow sleeves around, and the annular space of still flowing through between combustion liner 20 and flow sleeve 30 from the compressed air of compressor section 12.
In the combustion liner 20 shown in Fig. 2, Venturi tube 22 becomes angie type wall to form by two, and these two become angie type wall to divide 28 along the length formation reduced diameter portion of single wall formula combustion liner 20.Along the mobile compressed air of the annular space between combustion liner 20 and flow sleeve 30, by the outside of cool burner lining 20, this combustion liner 20 comprises that the reduced diameter portion that forms Venturi tube divides 28.
In order to ensure air stream, through guiding downward arrival reduced diameter portion to divide 28 outside, burner can comprise air deflector 70.In the embodiment shown in Figure 2, air deflector 70 comprises that two become angie type walls, and these two become angie type walls and formation combustion liner 20 reduced diameter portion to divide 28 two to become angie type wall almost parallel and aligning.The part air that air deflector deflected stream is crossed the annular space between combustion liner 20 and flow sleeve 30 enters reduced diameter portion downwards and divides the outer wall with the Venturi tube part of cooling single wall formula combustion liner 20.
As mentioned above, and return referring to accompanying drawing 1, double-walled venturi tube structure finally causes just in the position in Venturi tube inwall 24 tail end 27 downstreams, being transported to the combustion zone 95 of embodiment shown in Fig. 1 from the part air of compressor section.In order to provide similar air to flow in this position, in the embodiment shown in Figure 2, through single wall formula combustion liner 20, can form a plurality of dilution holes 74.
In the embodiment shown in Figure 2, dilution holes 74 forms ring-type around the outside of combustion liner 20.This allows air, and at certain position place, the annular space between combustion liner 20 and flow sleeve 30 flow into the inside of combustion liner 20, and this certain position is with roughly similar by the position of having carried for the cooling-air of cooling Venturi tube embodiment illustrated in fig. 1.Like this, being included in dilution holes 74 in embodiment illustrated in fig. 2 causes as in the embodiment shown in fig. 1 by the roughly similar combustion parameter presenting.
For deflecting down cooling-air, to the reduced diameter portion of single wall formula combustion liner 20, divide the air deflector 70 on 28 outsides can adopt multiple different form.Fig. 3 shows an embodiment, wherein, air deflector 70 forms two straight sections at an angle to each other, and wherein, these two straight sections are roughly parallel to and form the one-tenth angie type section 73,75 that single wall formula combustion liner 20 reduced diameter portion of Venturi tube are divided, and this embodiment is roughly similar to the embodiment shown in Fig. 2.
Combustion liner shown in Fig. 3 also comprises a plurality of flow spoiler rings 76.Flow spoiler ring 76 is for being formed on the projection on the outer surface of single wall formula combustion liner 20.Flow spoiler ring 76 extends around the outside of combustion liner 20.As shown in Figure 3, a plurality of this kind of flow spoiler rings 76 can be spaced apart from each other along the end section of combustion liner 20.
Flow spoiler ring flows through the annular space between combustion liner 20 and flow sleeve 30 compressed air for impelling forms turbulent air flow.Turbulent air flow contributes to strengthen the cooling effect being provided by this air, thereby reduces the bulk temperature of combustion liner 20.
Although the embodiment shown in Fig. 3 comprises even isolated five the flow spoiler rings of end section along combustion liner 20, the flow spoiler ring of varying number also can be set, and they can be differently spaced apart.And, replace, on the outside of combustion liner, projection is set, also by possible, thereby grooving strengthens cooling effect with turbulization air stream in the surface of combustion liner 20.In certain embodiments, can adopt groove and protruding combination to carry out turbulization air stream.No matter further, be different from concentric ring is set, be projection or depression, can also arrange and around the outside of combustion liner, not form a plurality of discrete raised or sunken of ring.
Embodiment shown in Fig. 4 is similar to the embodiment shown in Fig. 3.Yet in the embodiment shown in fig. 4, air deflector 70 comprises sweep, rather than straight one-tenth angie type part.Crooked air deflector can contribute to compressed-air actuated flowing as shown in Figure 4, or reduces flow resistance.
In addition, in the embodiment shown in fig. 4, the tail end of air deflector 70 extends beyond with head end the tail end that becomes angie type wall 73/75 and the head end that forms Venturi tube.Also will be likely, change any other parts of the disclosed embodiments, make the end of air deflector extend beyond head end and the tail end of Venturi tube.
In the embodiment shown in fig. 5, air deflector 70 is formed by the single straight section that is arranged on Venturi tube tail end place.In the view providing at Fig. 5 along the mobile air of annular space between combustion liner 20 and flow sleeve 30, will flow left.Like this, the air deflector in Fig. 5 70 deflects down part air stream by the one-tenth angie type part 73 and 75 being used for by Venturi tube and enters in the depression being formed on combustion liner 20 outsides.One denier air deflects down by this way, will realize most of cooling effect that the air stream by deflection provides.Like this, may need not arrange more than any object of the little air deflector 70 shown in Fig. 5 to reach well cooling that combustion liner 20 reduced diameter portion divide.
Fig. 6 shows and another embodiment similar shown in Fig. 5.Yet in the embodiment shown in fig. 6, the tail end of air deflector 70 is further caudad just extending upward than the rear wall of Venturi tube 75.In addition, the head end of air deflector 70 does not extend as the tail end of Venturi tube becomes angie type wall 75 in head-end direction always.And the air deflector slight curvature shown in Fig. 6 is to help leader air stream to divide to the reduced diameter portion of combustion liner 20 with the direction of expection.
Fig. 7 shows another embodiment of single wall formula combustion liner 20, and this single wall formula combustion liner 20 comprises by two one-tenth angie type wall 73,75 formed Venturi tubes.In this embodiment, air deflector is not set.Even be enough to coolingly become angie type wall 73,75 formed reduced diameter portion to divide by these two along the air stream of combustion liner outside.
This arranges flow spoiler ring 76 (or other analog structure) may be favourable at this position turbulization air stream for the tail end place dividing in reduced diameter portion.At this position turbulization air stream, can contribute to make part air stream to be deflected downwards to by one-tenth angie type wall 73, the 75 formed reduced diameter portion of Venturi tube divides.
Although the present invention is in conjunction with thinking that the most practical and preferred embodiment are described at present, but be to be understood that, the present invention is not limited to the disclosed embodiments, but in contrast, the present invention is intended to contain various modifications and the equivalent arrangements in the spirit and scope that are included in appended claims.

Claims (9)

1.一种用于涡轮发动机燃烧器的燃烧器衬套，包括：1. A combustor liner for a turbine engine combustor comprising: 从头端延伸到尾端的单壁式的大致圆柱形衬套；a single-walled, generally cylindrical bushing extending from head to tail; 形成在所述衬套的内部位于所述头端和所述尾端之间的文丘里管，所述文丘里管由如下部分构成：a venturi tube formed inside the bushing between the head end and the tail end, the venturi tube consisting of: 所述单壁式衬套的第一倾斜部分，其在向尾端方向上延伸时直径减小；以及a first sloped portion of the single-walled bushing that decreases in diameter as it extends in a caudal direction; and 所述单壁式衬套的第二倾斜部分，其在向尾端方向上延伸时直径增加，其中，所述第一倾斜部分的尾端连接到所述第二倾斜部分的头端上；a second sloped portion of the single-walled bushing that increases in diameter as it extends in a trailing direction, wherein the tail end of the first sloped portion is connected to the head end of the second sloped portion; 所述燃烧器衬套还包括安装在所述单壁式的大致圆柱形衬套的外部上的空气偏导器，使得在所述空气偏导器和所述大致圆柱形衬套之间具有环形空间，其中，所述空气偏导器构造成用以将沿着所述圆柱形衬套的外部从所述尾端向所述头端流过的部分空气流偏转到由所述第一倾斜部分和所述第二倾斜部分所形成在所述衬套的外部上的环形凹陷上。The combustor liner also includes an air deflector mounted on the exterior of the single-walled generally cylindrical liner such that there is an annular space, wherein the air deflector is configured to deflect a portion of the air flow passing along the exterior of the cylindrical liner from the trailing end to the leading end toward the first inclined portion and the second sloped portion are formed on the annular recess on the exterior of the bush. 2.根据权利要求1所述的燃烧器衬套，其特征在于，所述大致圆柱形衬套包括连接到所述第二倾斜部分的尾端上的尾端圆柱形部分，以及其中，在所述尾端圆柱形部分中形成多个稀释孔。2. The combustor liner of claim 1 , wherein said generally cylindrical liner includes a trailing cylindrical portion connected to a trailing end of said second sloped portion, and wherein said A plurality of dilution holes are formed in the cylindrical portion of the tail. 3.根据权利要求2所述的燃烧器衬套，其特征在于，所述多个稀释孔布置成围绕所述尾端圆柱形部分的圆周延伸的环，以及其中，由稀释孔形成的环在向尾端方向上远离所述第二倾斜部分的尾端间隔开。3. The combustor liner of claim 2, wherein the plurality of dilution holes are arranged in a ring extending around the circumference of the trailing end cylindrical portion, and wherein the ring formed by the dilution holes is at Spaced away from the trailing end of the second sloped portion in a trailing direction. 4.根据权利要求1所述的燃烧器衬套，其特征在于，所述大致圆柱形衬套包括连接到所述第二倾斜部分的尾端上的尾端圆柱形部分，以及其中，至少一个扰流器环位于所述尾端圆柱形部分上，各至少一个扰流器环均从所述尾端圆柱形部分的外部凸出且围绕所述尾端圆柱形部分的圆周延伸。4. The combustor liner of claim 1, wherein said generally cylindrical liner includes a trailing cylindrical portion connected to a trailing end of said second sloped portion, and wherein at least one Spoiler rings are located on the trailing cylindrical portion, each at least one spoiler ring protruding from the exterior of the trailing cylindrical portion and extending around the circumference of the trailing cylindrical portion. 5.根据权利要求4所述的燃烧器衬套，其特征在于，所述至少一个扰流器环包括沿所述尾端圆柱形部分彼此间隔开的多个扰流器环。5. The combustor liner of claim 4, wherein said at least one spoiler ring comprises a plurality of spoiler rings spaced apart from one another along said trailing cylindrical portion. 6.根据权利要求1所述的燃烧器衬套，其特征在于，所述空气偏导器包括：6. The combustor liner of claim 1 wherein said air deflector comprises: 第一倾斜部分，其在向尾端方向上延伸时直径减小，其中，所述空气偏导器的第一倾斜部分与所述衬套的第一倾斜部分对准；以及a first angled portion that decreases in diameter as it extends in an aft direction, wherein the first angled portion of the air deflector is aligned with the first angled portion of the bushing; and 第二倾斜部分，其在在向尾端方向上延伸时直径增加，其中，所述空气偏导器的第一倾斜部分的尾端连接到所述空气偏导器的第二倾斜部分的头端上，以及其中，所述空气偏导器的第二倾斜部分与所述衬套的第二倾斜部分对准。a second sloped portion that increases in diameter as it extends in a tailward direction, wherein the tail end of the first sloped portion of the air deflector is connected to the head end of the second sloped portion of the air deflector , and wherein the second sloped portion of the air deflector is aligned with the second sloped portion of the bushing. 7.根据权利要求6所述的燃烧器衬套，其特征在于，所述空气偏导器的第一倾斜部分的头端在向头端方向上延伸超出所述圆柱形衬套的第一倾斜部分的头端。7. The combustor liner of claim 6, wherein the head end of the first angled portion of the air deflector extends in the head end direction beyond the first angled portion of the cylindrical liner. part of the head. 8.根据权利要求7所述的燃烧器衬套，其特征在于，所述空气偏导器的第二倾斜部分的尾端在向尾端方向上延伸超出所述圆柱形衬套的第二倾斜部分的尾端。8. The combustor liner of claim 7, wherein the aft end of the second sloped portion of the air deflector extends in an aft direction beyond the second sloped portion of the cylindrical liner. part end. 9.根据权利要求6所述的燃烧器衬套，其特征在于，所述空气偏导器的第二倾斜部分的尾端在向尾端方向上延伸超出所述圆柱形衬套的第二倾斜部分的尾端。9. The combustor liner of claim 6, wherein the aft end of the second sloped portion of the air deflector extends in an aft direction beyond the second sloped portion of the cylindrical liner. part end.
CN201110087119.3A 2010-02-19 2011-02-18 Combustor liners for turbine engines Expired - Fee Related CN102213425B (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US12/708,736 US8646277B2 (en) 2010-02-19 2010-02-19 Combustor liner for a turbine engine with venturi and air deflector
US12/708736 2010-02-19

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CN102213425A CN102213425A (en) 2011-10-12
CN102213425B true CN102213425B (en) 2014-11-19

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US (1) US8646277B2 (en)
JP (1) JP5911672B2 (en)
CN (1) CN102213425B (en)
CH (1) CH702738B1 (en)
DE (1) DE102011000788A1 (en)

Families Citing this family (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20120047895A1 (en) * 2010-08-26 2012-03-01 General Electric Company Systems and apparatus relating to combustor cooling and operation in gas turbine engines
US9134028B2 (en) * 2012-01-18 2015-09-15 Pratt & Whitney Canada Corp. Combustor for gas turbine engine
US20130318986A1 (en) * 2012-06-05 2013-12-05 General Electric Company Impingement cooled combustor
US9664390B2 (en) 2012-07-09 2017-05-30 Ansaldo Energia Switzerland AG Burner arrangement including an air supply with two flow passages
US9897317B2 (en) * 2012-10-01 2018-02-20 Ansaldo Energia Ip Uk Limited Thermally free liner retention mechanism
US9869279B2 (en) * 2012-11-02 2018-01-16 General Electric Company System and method for a multi-wall turbine combustor
US20150362192A1 (en) * 2013-01-17 2015-12-17 United Technologies Corporation Gas turbine engine combustor liner assembly with convergent hyperbolic profile
CN103528094B (en) * 2013-07-10 2015-04-08 辽宁省燃烧工程技术中心（有限公司） Dry-type low-nitrogen combustion device for gas fuel of gas turbine
US9625158B2 (en) * 2014-02-18 2017-04-18 Dresser-Rand Company Gas turbine combustion acoustic damping system
JP6267085B2 (en) * 2014-09-05 2018-01-24 三菱日立パワーシステムズ株式会社 Gas turbine combustor
CN104654297B (en) * 2014-12-24 2017-04-05 二重集团（德阳）重型装备股份有限公司 Flame heats shower nozzle
US10253690B2 (en) * 2015-02-04 2019-04-09 General Electric Company Turbine system with exhaust gas recirculation, separation and extraction
US10316746B2 (en) * 2015-02-04 2019-06-11 General Electric Company Turbine system with exhaust gas recirculation, separation and extraction
US10465907B2 (en) * 2015-09-09 2019-11-05 General Electric Company System and method having annular flow path architecture
US10228141B2 (en) 2016-03-04 2019-03-12 General Electric Company Fuel supply conduit assemblies
US10203114B2 (en) * 2016-03-04 2019-02-12 General Electric Company Sleeve assemblies and methods of fabricating same
US10337738B2 (en) * 2016-06-22 2019-07-02 General Electric Company Combustor assembly for a turbine engine
US11022313B2 (en) 2016-06-22 2021-06-01 General Electric Company Combustor assembly for a turbine engine
US10655859B2 (en) 2017-01-11 2020-05-19 Honeywell International Inc. Turbine scroll assembly for gas turbine engine
US10598380B2 (en) 2017-09-21 2020-03-24 General Electric Company Canted combustor for gas turbine engine
US11306918B2 (en) * 2018-11-02 2022-04-19 Chromalloy Gas Turbine Llc Turbulator geometry for a combustion liner
JP7132096B2 (en) * 2018-11-14 2022-09-06 三菱重工業株式会社 gas turbine combustor
US11181269B2 (en) 2018-11-15 2021-11-23 General Electric Company Involute trapped vortex combustor assembly
US11079111B2 (en) 2019-04-29 2021-08-03 Solar Turbines Incorporated Air tube
CN116265810A (en) * 2021-12-16 2023-06-20 通用电气公司 Swirler counter dilution with shaped cooling fence
US11835236B1 (en) 2022-07-05 2023-12-05 General Electric Company Combustor with reverse dilution air introduction

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3907489A (en) * 1974-10-03 1975-09-23 Selas Corp Of America Noise suppressor for burner
US3927958A (en) * 1974-10-29 1975-12-23 Gen Motors Corp Recirculating combustion apparatus
US5454221A (en) * 1994-03-14 1995-10-03 General Electric Company Dilution flow sleeve for reducing emissions in a gas turbine combustor
CN1637248A (en) * 2004-01-06 2005-07-13 通用电气公司 Apparatus and methods for minimizing and/or eliminating dilution air leakage in a combustion liner assembly
CN101349425A (en) * 2007-07-16 2009-01-21 通用电气公司 Apparatus/method for cooling combustion chamber/venturi in a low NOx combustor

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3938324A (en) * 1974-12-12 1976-02-17 General Motors Corporation Premix combustor with flow constricting baffle between combustion and dilution zones
US4292801A (en) * 1979-07-11 1981-10-06 General Electric Company Dual stage-dual mode low nox combustor
US4845940A (en) * 1981-02-27 1989-07-11 Westinghouse Electric Corp. Low NOx rich-lean combustor especially useful in gas turbines
US5117636A (en) * 1990-02-05 1992-06-02 General Electric Company Low nox emission in gas turbine system
US5253478A (en) * 1991-12-30 1993-10-19 General Electric Company Flame holding diverging centerbody cup construction for a dry low NOx combustor
US6427446B1 (en) * 2000-09-19 2002-08-06 Power Systems Mfg., Llc Low NOx emission combustion liner with circumferentially angled film cooling holes
EP1461520A4 (en) * 2001-11-30 2010-04-14 Power Systems Mfg Llc COMBUSTION CHAMBER / VENTURI COOLING FOR LOW NOX EMISSION COMBUSTION DEVICE
US6772595B2 (en) * 2002-06-25 2004-08-10 Power Systems Mfg., Llc Advanced cooling configuration for a low emissions combustor venturi
US6865892B2 (en) * 2002-12-17 2005-03-15 Power Systems Mfg, Llc Combustion chamber/venturi configuration and assembly method
US7389643B2 (en) * 2005-01-31 2008-06-24 General Electric Company Inboard radial dump venturi for combustion chamber of a gas turbine
US7513115B2 (en) * 2005-05-23 2009-04-07 Power Systems Mfg., Llc Flashback suppression system for a gas turbine combustor
US8028529B2 (en) * 2006-05-04 2011-10-04 General Electric Company Low emissions gas turbine combustor
US8707704B2 (en) 2007-05-31 2014-04-29 General Electric Company Method and apparatus for assembling turbine engines
US20090053054A1 (en) * 2007-08-20 2009-02-26 General Electric Company LEAKAGE REDUCING VENTURI FOR DRY LOW NITRIC OXIDES (NOx) COMBUSTORS
US7712314B1 (en) * 2009-01-21 2010-05-11 Gas Turbine Efficiency Sweden Ab Venturi cooling system

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3907489A (en) * 1974-10-03 1975-09-23 Selas Corp Of America Noise suppressor for burner
US3927958A (en) * 1974-10-29 1975-12-23 Gen Motors Corp Recirculating combustion apparatus
US5454221A (en) * 1994-03-14 1995-10-03 General Electric Company Dilution flow sleeve for reducing emissions in a gas turbine combustor
CN1637248A (en) * 2004-01-06 2005-07-13 通用电气公司 Apparatus and methods for minimizing and/or eliminating dilution air leakage in a combustion liner assembly
CN101349425A (en) * 2007-07-16 2009-01-21 通用电气公司 Apparatus/method for cooling combustion chamber/venturi in a low NOx combustor

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US8646277B2 (en) 2014-02-11
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